Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: A method and a device for detecting a fault in a mechanical system comprising a rotating member and a vibration sensor transmitting a temporal vibration signal. The method comprises processing the temporal vibration signals transmitted over a predetermined period in order to transform the temporal vibration signals firstly into angular vibration signals, then into frequency vibration signals. Next, series of amplitudes are generated, each series being associated with a specific frequency channel and comprising the amplitudes of the frequency vibration signals for this frequency channel. The frequency channels displaying an increasing trend consistent with the fault of interest are then identified. The frequency channels that display an increasing trend are then compared with characteristic frequencies of a known fault of interest in order to check for the possible presence of such a fault in the mechanical system.

Abstract: A method for determining the cyclostationarity of a vibration signal transmitted by a vibration sensor arranged on a mechanical system and allowing a cyclostationarity indicator I? to be calculated. The present disclosure also relates to a method for arranging vibration sensors, using the method for determining cyclostationarity applied to the signals transmitted by these vibration sensors at different positions and orientations. A position of a vibration sensor is validated as a function of this cyclostationarity indicator I?. The present disclosure finally relates to a method for monitoring a mechanical system 10 using the method for determining cyclostationarity to determine the cyclostationarity of the vibration signals relating to the mechanical system before calculating the monitoring indicators of the mechanical system.

Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: A suspension device provided with at least one suspension means. The suspension means comprise a tuned mass damper, the damper comprising an inertial mass carried by a mass support. The suspension means include at least a first actuator generating a dynamic force for acting on the swinging motion of the damper. The inertial mass being movable longitudinally in translation relative to the mass support, the suspension device including a second actuator connected to the inertial mass to move the inertial mass longitudinally relative to the mass support.

Abstract: A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.

Abstract: A suspension device provided with at least one suspension means. The suspension means comprise a tuned mass damper, the damper comprising an inertial mass carried by a mass support. The suspension means include at least a first actuator generating a dynamic force for acting on the swinging motion of the damper. The inertial mass being movable longitudinally in translation relative to the mass support, the suspension device including a second actuator connected to the inertial mass to move the inertial mass longitudinally relative to the mass support.

Abstract: A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.